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EPPLER E853 AIRFOIL (e853-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER E853 AIRFOIL (e853-il)
Reynolds number: 500,000
Max Cl/Cd: 102.98 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e853-il-500000-n5.txt
Download as CSV file: xf-e853-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E853 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5012   0.04228   0.03974  -0.0885   0.9789   0.0033
  -8.750  -0.5214   0.03097   0.02762  -0.0942   0.9602   0.0030
  -8.500  -0.5113   0.02585   0.02191  -0.0956   0.9490   0.0029
  -8.250  -0.4882   0.02253   0.01812  -0.0973   0.9423   0.0029
  -8.000  -0.4610   0.02021   0.01544  -0.0989   0.9351   0.0030
  -7.750  -0.4269   0.01831   0.01321  -0.1014   0.9306   0.0030
  -7.500  -0.3927   0.01673   0.01139  -0.1038   0.9233   0.0031
  -7.250  -0.3548   0.01543   0.00987  -0.1068   0.9168   0.0032
  -7.000  -0.3194   0.01435   0.00862  -0.1091   0.9066   0.0033
  -6.750  -0.2857   0.01344   0.00754  -0.1109   0.8950   0.0035
  -6.500  -0.2544   0.01272   0.00664  -0.1121   0.8817   0.0038
  -6.250  -0.2255   0.01213   0.00589  -0.1127   0.8680   0.0042
  -6.000  -0.1977   0.01169   0.00527  -0.1130   0.8547   0.0046
  -5.750  -0.1710   0.01116   0.00460  -0.1131   0.8424   0.0057
  -5.500  -0.1441   0.01083   0.00416  -0.1131   0.8309   0.0075
  -5.250  -0.1175   0.01048   0.00376  -0.1131   0.8200   0.0132
  -5.000  -0.0909   0.01017   0.00344  -0.1131   0.8095   0.0245
  -4.750  -0.0641   0.00988   0.00316  -0.1132   0.8001   0.0383
  -4.500  -0.0373   0.00959   0.00290  -0.1133   0.7913   0.0604
  -4.250  -0.0104   0.00931   0.00264  -0.1133   0.7826   0.0878
  -4.000   0.0165   0.00898   0.00240  -0.1135   0.7745   0.1282
  -3.750   0.0434   0.00863   0.00217  -0.1137   0.7670   0.1826
  -3.500   0.0704   0.00820   0.00194  -0.1140   0.7597   0.2579
  -3.000   0.1247   0.00761   0.00173  -0.1144   0.7460   0.4135
  -2.750   0.1525   0.00757   0.00168  -0.1144   0.7398   0.4408
  -2.500   0.1805   0.00755   0.00164  -0.1145   0.7337   0.4566
  -2.250   0.2083   0.00754   0.00160  -0.1145   0.7277   0.4718
  -2.000   0.2362   0.00753   0.00158  -0.1146   0.7221   0.4903
  -1.750   0.2642   0.00753   0.00158  -0.1147   0.7165   0.5067
  -1.250   0.3202   0.00756   0.00154  -0.1148   0.7062   0.5245
  -1.000   0.3481   0.00757   0.00153  -0.1149   0.7010   0.5304
  -0.750   0.3761   0.00760   0.00153  -0.1150   0.6965   0.5365
  -0.500   0.4042   0.00761   0.00154  -0.1151   0.6915   0.5421
  -0.250   0.4321   0.00763   0.00156  -0.1151   0.6866   0.5481
   0.000   0.4601   0.00767   0.00157  -0.1152   0.6824   0.5542
   0.250   0.4881   0.00768   0.00161  -0.1153   0.6777   0.5602
   0.500   0.5160   0.00772   0.00164  -0.1154   0.6731   0.5668
   0.750   0.5438   0.00775   0.00170  -0.1154   0.6690   0.5730
   1.000   0.5718   0.00778   0.00175  -0.1155   0.6644   0.5801
   1.250   0.5996   0.00781   0.00182  -0.1156   0.6597   0.5870
   1.500   0.6273   0.00787   0.00188  -0.1156   0.6554   0.5945
   1.750   0.6549   0.00789   0.00198  -0.1156   0.6495   0.6020
   2.000   0.6821   0.00795   0.00205  -0.1155   0.6426   0.6103
   2.250   0.7092   0.00798   0.00213  -0.1154   0.6342   0.6189
   2.500   0.7359   0.00804   0.00223  -0.1152   0.6251   0.6278
   2.750   0.7623   0.00811   0.00232  -0.1149   0.6139   0.6377
   3.000   0.7882   0.00817   0.00242  -0.1146   0.5996   0.6480
   3.250   0.8137   0.00825   0.00252  -0.1141   0.5810   0.6586
   3.500   0.8393   0.00835   0.00264  -0.1137   0.5643   0.6706
   3.750   0.8643   0.00847   0.00280  -0.1132   0.5456   0.6836
   4.000   0.8887   0.00863   0.00296  -0.1125   0.5206   0.6974
   4.250   0.9109   0.00891   0.00317  -0.1115   0.4813   0.7124
   4.500   0.9292   0.00945   0.00348  -0.1098   0.4164   0.7293
   4.750   0.9431   0.01038   0.00402  -0.1074   0.3259   0.7481
   5.000   0.9577   0.01127   0.00459  -0.1053   0.2441   0.7689
   5.250   0.9746   0.01196   0.00511  -0.1035   0.1880   0.7933
   5.750   1.0079   0.01292   0.00599  -0.0995   0.1166   0.8710
   6.000   1.0232   0.01330   0.00636  -0.0971   0.0886   1.0000
   6.250   1.0429   0.01387   0.00683  -0.0959   0.0673   1.0000
   6.500   1.0629   0.01439   0.00729  -0.0947   0.0514   1.0000
   6.750   1.0816   0.01499   0.00780  -0.0933   0.0363   1.0000
   7.000   1.0997   0.01561   0.00837  -0.0918   0.0238   1.0000
   7.250   1.1173   0.01622   0.00893  -0.0902   0.0150   1.0000
   7.500   1.1346   0.01675   0.00947  -0.0885   0.0108   1.0000
   7.750   1.1509   0.01732   0.01006  -0.0867   0.0077   1.0000
   8.000   1.1652   0.01802   0.01077  -0.0845   0.0053   1.0000
   8.250   1.1805   0.01867   0.01149  -0.0825   0.0042   1.0000
   8.500   1.1947   0.01940   0.01228  -0.0804   0.0035   1.0000
   8.750   1.2068   0.02029   0.01325  -0.0781   0.0029   1.0000
   9.000   1.2184   0.02124   0.01429  -0.0757   0.0027   1.0000
   9.250   1.2305   0.02216   0.01532  -0.0735   0.0025   1.0000
   9.500   1.2420   0.02313   0.01639  -0.0714   0.0025   1.0000
   9.750   1.2524   0.02421   0.01761  -0.0692   0.0024   1.0000
  10.000   1.2619   0.02539   0.01890  -0.0670   0.0023   1.0000
  10.250   1.2702   0.02673   0.02036  -0.0648   0.0022   1.0000
  10.500   1.2783   0.02811   0.02186  -0.0627   0.0022   1.0000
  10.750   1.2855   0.02964   0.02352  -0.0607   0.0021   1.0000
  11.000   1.2922   0.03127   0.02528  -0.0587   0.0021   1.0000
  11.250   1.2984   0.03302   0.02716  -0.0569   0.0020   1.0000
  11.500   1.3035   0.03494   0.02924  -0.0552   0.0020   1.0000
  11.750   1.3082   0.03697   0.03142  -0.0535   0.0020   1.0000
  12.000   1.3117   0.03920   0.03381  -0.0520   0.0020   1.0000
  12.250   1.3138   0.04163   0.03642  -0.0506   0.0020   1.0000
  12.500   1.3150   0.04424   0.03922  -0.0493   0.0019   1.0000
  12.750   1.3144   0.04711   0.04227  -0.0482   0.0019   1.0000
  13.000   1.3120   0.05028   0.04565  -0.0472   0.0019   1.0000
  13.250   1.3079   0.05373   0.04932  -0.0466   0.0019   1.0000
  13.500   1.3019   0.05753   0.05333  -0.0462   0.0019   1.0000
  13.750   1.2935   0.06179   0.05781  -0.0462   0.0019   1.0000
  14.000   1.2842   0.06633   0.06256  -0.0466   0.0019   1.0000
  14.250   1.2730   0.07141   0.06783  -0.0476   0.0019   1.0000
  14.500   1.2605   0.07697   0.07360  -0.0491   0.0019   1.0000
  14.750   1.2460   0.08319   0.08002  -0.0512   0.0019   1.0000
  15.000   1.2299   0.09012   0.08716  -0.0542   0.0019   1.0000
  15.250   1.2119   0.09798   0.09521  -0.0580   0.0019   1.0000
  15.500   1.1923   0.10679   0.10422  -0.0628   0.0019   1.0000
  15.750   1.1723   0.11648   0.11410  -0.0685   0.0019   1.0000
  16.000   1.1485   0.12812   0.12593  -0.0757   0.0020   1.0000
  16.250   1.1225   0.14146   0.13944  -0.0840   0.0020   1.0000
  16.500   1.0930   0.15717   0.15530  -0.0933   0.0021   1.0000
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